Search

CN-116834323-B - Integral heat-proof structure with ablation and heat-insulating functional partitions and preparation method thereof

CN116834323BCN 116834323 BCN116834323 BCN 116834323BCN-116834323-B

Abstract

S1, loading an ablation layer chopped fiber premix into a female mold, and performing molding, preforming and curing to obtain an ablation layer preform; S2, machining an inner surface of the ablation layer prefabricated body, S3, paving the low-density prepreg cloth of the heat insulation layer on the inner surface, S4, performing molding, preforming and curing to obtain the heat insulation layer-ablation layer prefabricated body, S5, machining the inner surface of the heat insulation layer, S6, demolding to obtain the integral heat-proof structure with ablation and heat insulation function areas. According to the preparation method, the chopped fiber premix is adopted to prepare the ablation layer outside, the ablation layer can meet the temperature tolerance requirement, the low-density prepreg is adopted to prepare the heat insulation layer inside, the working temperature requirements of a bearing structure and equipment in an inner cabin can be met, and meanwhile the lightening requirement of a heat-proof structure is met.

Inventors

  • ZHANG YUSEN
  • REN LIANG

Assignees

  • 北京玻钢院复合材料有限公司

Dates

Publication Date
20260512
Application Date
20230628

Claims (7)

  1. 1. The preparation method of the integral heat-proof structure with the ablation and heat-insulation functional partitions is characterized by comprising the following steps of: s1, loading an ablation layer chopped fiber premix into a female die, and performing primary molding, preforming and curing to obtain an ablation layer preform; S2, carrying out first machining on the inner surface of the ablation layer preform; s3, paving the low-density prepreg cloth of the heat insulation layer on the inner molded surface of the ablation layer preform after the first machining to obtain a heat insulation layer paving sheet-ablation layer preform combination; S4, performing secondary molding, preforming and curing on the thermal insulation layer paving sheet-ablation layer preform assembly to obtain a thermal insulation layer-ablation layer preform; s5, carrying out secondary machining on the inner shape surface of the heat insulation layer-ablation layer prefabricated body; s6, demolding the thermal insulation layer-ablation layer prefabricated body to obtain the integral heat-proof structure with the ablation and thermal insulation function partitions; The step S1 specifically comprises the following steps: s101, filling an ablative layer chopped fiber premix into a premix preforming container to prepare an ablative layer premix filling block; S102, filling the ablation layer premix filling blocks into a female mold, and packaging the ablation layer premix filling blocks by using a molding gum cover to obtain an ablation layer premix filling block-female mold packaging combination; s103, vacuumizing the ablative layer premix filling block-female die packaging assembly; S104, performing primary molding, preforming and curing on the ablation layer premix filling block-female die mold packaging assembly to obtain an ablation layer preform; In the step S1, the curing condition in the first molding preforming curing is that the pressure is increased to 3.7-4MPa at the rate of 1MPa/10min, the temperature is increased to 85-95 ℃ at the rate of 5-10 ℃/10min, and the temperature is kept for 180-200min; In the step S4, the curing condition in the second molding and preforming curing is that the pressure is increased to 3.7-4MPa at the rate of 1MPa/10min, the temperature is increased to 90-100 ℃ at the rate of 5-10 ℃/10min, the temperature is kept for 60-80min, then the temperature is increased to 120-130 ℃ at the rate of 5-10 ℃/10min, the temperature is kept for 120-130min, the temperature is increased to 150-155 ℃ at the rate of 5-10 ℃/10min, and the temperature is kept for 480-500min.
  2. 2. The method of manufacturing according to claim 1, characterized in that: The step S101 specifically comprises the steps of filling the ablation layer chopped fiber premix into a premix preforming container, airing at room temperature for 24-28h, and then vacuumizing and preserving for 1-2h to obtain the ablation layer premix filling block.
  3. 3. The method of manufacturing according to claim 1, characterized in that: in step S102, after filling the ablation layer premix filling blocks into a female mold, vacuumizing and shaping for 1-2h.
  4. 4. The method of manufacturing according to claim 1, characterized in that: Step S103 specifically includes the following steps: And storing the ablation layer premix filling block-female die packaging assembly for 3-4 hours at 90 ℃ and minus 0.08 MPa.
  5. 5. The method of manufacturing according to claim 1, characterized in that: The step S4 specifically comprises the following steps: S401, packaging the thermal insulation layer paving sheet-ablation layer preform assembly by using a molding rubber sleeve to obtain a thermal insulation layer paving sheet-ablation layer preform packaging assembly; S402, vacuumizing the thermal insulation layer paving sheet-ablation layer preform packaging assembly; s403, performing secondary molding, preforming and curing on the thermal insulation layer paving sheet-ablation layer preform packaging assembly to obtain the thermal insulation layer-ablation layer preform.
  6. 6. The method of manufacturing according to claim 1, characterized in that: The density of the ablation layer chopped fiber premix is 1400-1600kg/m 3 , and the density of the thermal insulation layer low-density prepreg is 800-1200kg/m 3 .
  7. 7. An ablative, thermally insulating, functional partitioned, monolithic thermal protection structure prepared by the method of any one of claims 1-6.

Description

Integral heat-proof structure with ablation and heat-insulating functional partitions and preparation method thereof Technical Field The invention belongs to the technical field of heat-proof structures of high-speed aircrafts, and particularly relates to an integral heat-proof structure with ablation and heat-insulation functional partitions and a preparation method thereof. Background In the technical field of high-speed aircrafts, based on aerodynamics, the working environment temperature can reach tens of thousands of DEG C, and no single material can withstand such high temperature at present, so that the equipment periphery of the high-speed aircrafts adopts a polymer composite material with a certain thickness for ablation heat protection. The equipment in the engineering field has the highest peripheral working temperature reaching 2000 deg.c and long-term working temperature over 1000 deg.c, but its bearing structure has working temperature less than 200 deg.c and inner cabin equipment working temperature less than 60 deg.c, and the outer ablation layer is assembled with other components, so that the outer surface of the heat protecting structure is special structure. For the design of high-speed aircrafts, weight is an important index for checking the equipment advancement, and light weight is an important development direction in the field. At present, as for a thermal protection layer of a high-speed aircraft, a single-layer composite material ablation structure is mostly adopted, for example, chinese patent literature with publication number of CN 111114750A discloses a thermal protection device and a reentry aircraft, wherein the thermal protection device comprises a rigid or flexible thermal insulation layer made of fibers, one side of the thermal insulation layer is connected with a thermal protection cover plate, the thermal protection layer composite material of the aircraft can bear the high temperature of l760 ℃, and the supporting structure can bear the temperature and stress conditions of 1350-1600 ℃. However, to realize normal operation of engineering equipment under the working conditions that the highest peripheral working temperature is approximately 2000 ℃, the long-time working temperature is above 1000 ℃, the working temperature of a bearing structure is less than 200 ℃ and the working temperature of internal cabin equipment is less than 60 ℃, the traditional single-layer composite material ablation structure cannot meet the weight index requirements on the premise of meeting the ablation resistance and heat insulation functional requirements. Therefore, how to prepare the heat-proof structure of the high-speed aircraft so as to meet the temperature tolerance requirement of the aircraft, the working temperature requirement of equipment in the bearing structure and the inner cabin and the lightening requirement of the high-speed aircraft, and meanwhile, the problem that the external profile of the heat-proof structure is designed into a special-shaped structure is needed to be solved at present. Disclosure of Invention The technical problem solved by the invention is that the heat-proof structure of the high-speed aircraft is difficult to simultaneously meet the temperature tolerance requirement, the load-carrying structure, the equipment working temperature requirement in the inner cabin and the aircraft lightening requirement, so that the integral heat-proof structure with ablation and heat insulation function partitions and the preparation method thereof are provided, an ablation layer is prepared by adopting an ablation-resistant chopped fiber premix outside, the ablation layer can meet the temperature tolerance requirement, a heat insulation layer is prepared by adopting low-density prepreg inside, the load-carrying structure and the equipment working temperature requirement in the inner cabin are met, the lightening requirement of the heat-proof structure is met, and the special structural design of the outer ablation-resistant layer can be realized by adopting the pre-filling of the chopped fiber premix in a female die for pre-curing forming. In order to solve the above problems, a first aspect of the present invention provides a method for preparing an integral heat-proof structure with ablation and heat-proof function, comprising the following steps: s1, loading an ablation layer chopped fiber premix into a female die, and performing primary molding, preforming and curing to obtain an ablation layer preform; S2, carrying out first machining on the inner surface of the ablation layer preform; s3, paving the low-density prepreg cloth of the heat insulation layer on the inner molded surface of the ablation layer preform after the first machining to obtain a heat insulation layer paving sheet-ablation layer preform combination; S4, performing secondary molding, preforming and curing on the thermal insulation layer paving sheet-ablation layer preform assembly to obtain a ther